Device for managing the mechanical energy of an aircraft, with a force application system on a control lever, related aircraft and process

ABSTRACT

A device for managing the mechanical energy of an aircraft, with a force application system on a control lever, includes a support defining a guide; a moving control lever for controlling varying a mechanical energy variation of the aircraft, mounted moving through the guide; and at least one position sensor detecting the position of the moving lever in the guide, configured to create position information for the position of the moving lever in the guide intended to be sent to a flight control unit of the aircraft. The device also includes an active force applicator for applying a force on the moving lever, configured to generate a force applied on the moving lever. The force depends on the position of the moving lever in the guide.

This claims the benefit of French Patent Application FR 16 01611, filedNov. 14, 2016 and hereby incorporated by reference herein.

The Detailed Description and drawings of the present application werealso filed in a U.S. patent application identified by Ser. No.15/809,374, entitled DEVICE FOR MANAGING THE MECHANICAL ENERGY OF ANAIRCRAFT, HAVING AN ENERGY MANAGEMENT AUXILIARY SYSTEM, RELATED AIRCRAFTAND PROCESS, filed on the same date as the present application, and in aU.S. patent application identified by Ser. No. 15/809,385, entitled Ser.No. 15/809,388, entitled DEVICE FOR MANAGING THE MECHANICAL ENERGY OF ANAIRCRAFT, HAVING A LIGHT SYSTEM, RELATED AIRCRAFT AND PROCESS, filed onthe same date as the present application.

The present disclosure relates to a device for managing the mechanicalenergy of an aircraft, intended to be placed in a cockpit of theaircraft, comprising:

-   -   a support defining a guide;    -   a moving control lever for varying the mechanical energy of the        aircraft, mounted moving through the guide;    -   at least one position sensor detecting the position of the        moving lever in the guide, able to create position information        for the position of the moving lever in the guide intended to be        sent to a flight control unit of the aircraft able to control        jointly, based on position information of the moving lever, at        least one propulsion motor and at least one member modifying the        energy of the aircraft.

The cockpit of the aircraft is for example situated in the aircraft, inthe front thereof, or on the ground, in a control booth separated fromthe aircraft or in a stimulator.

Such a device is in particular intended to facilitate piloting of thepropulsion axis of the aircraft, while simplifying the pilot's task.

BACKGROUND

Generally, in aircrafts, the propulsion axis is piloted by severalcontrols, in particular the throttle corresponding to each motor, and bycontrols controlling the members for modifying the energy of theaircraft, such as the air brakes and the foil flaps.

To modify the total mechanical energy of the aircraft, the pilot can acton the throttles. However, he can only view the result of his set-pointin terms of acceleration and gradient once the motor speed hasstabilized.

Furthermore, the perception of the variation of mechanical energyavailable in the aircraft at a given moment resulting from the availablethrust or braking controls is delicate, and is only obtained indirectly,for example by observing the motor speed percentage on a display in thecockpit.

To offset this problem, U.S. Pat. No. 8,527,173 describes a device formanaging the total energy of an aircraft in which a lever can be used toadjust an energy variation of the aircraft, comparable to a pseudo-totalgradient of the aircraft.

Based on the energy variation control signal sent to the flight controlunit, the latter adjusts the motor speed of each motor and the drag toreach the adjusted energy variation.

Furthermore, a possible energy variation scale is displayed in the formof a pseudo-gradient scale on a display of the aircraft. This scale isbounded upwardly and downwardly, respectively, by the maximum andminimum energy variation values that can be achieved by the aircraft,allowing the pilot to evaluate the operational situation on thepropulsion axis and the energy variation availability.

SUMMARY OF THE INVENTION

This visual information is very useful for the pilot. However, in someoperational situations, in particular when the pilot must control otherflight parameters, he cannot concentrate directly on a scale displayedon a display.

One aim of the invention is therefore to have a management device thatprovides, at all times, an indication of the aircraft's situation interms of propulsion in its capacity range, when the pilot is unable tocarefully observe a display in the cockpit.

To that end, a device of the aforementioned type is provided,characterized in that it includes an active system for applying a forceon the moving lever, able to generate a force applied on the movinglever, the applied force depending on at least the position of themoving lever in the guide.

The device may comprise one or more of the following features,considered alone or according to any technically possible combination:

-   -   the active system for applying a force is able to generate, in        the absence of outside maneuvering of the moving lever by a        user, a force for moving the moving lever in the guide to a        movable neutral position advantageously representative of the        current mechanical energy variation of the aircraft in a range        of possible mechanical energy variations for the aircraft;    -   the active system for applying a force is able to generate a        force profile during maneuvering of the moving lever by a user;    -   the force profile includes a stable detent, an unstable detent,        and/or a ramp;    -   the active application system comprises an actuator, able to act        on the moving lever to generate the applied force and a control        unit of the actuator, able to control the actuator at least        based on the position information of the moving lever;    -   the actuator includes a motor having an output shaft mounted        rotating around the shaft axis, the device comprising a        transmission mechanism connecting the motor to the moving lever;    -   the moving lever is mounted rotating in the guide around a        moving lever rotation axis non parallel to the shaft axis, the        transmission mechanism comprising at least one intermediate        connecting rod, having a first end movable jointly in rotation        with the shaft axis and a second end movable jointly in rotation        with the moving lever rotation axis;    -   an auxiliary assembly for applying a mechanical force on the        moving lever, able to switch spontaneously between a deactivated        configuration when the active system for applying a force is        active and an active configuration, when the active system for        applying a force is deactivated;    -   the mechanical force is a friction force, the auxiliary assembly        for applying a mechanical force including at least one pad        movable between a position engaged on the moving lever in the        active configuration and a position disengaged from the moving        lever in the deactivated configuration;    -   the auxiliary assembly for applying a mechanical force includes        a member for elastically biasing the moving pad toward the        engaged position and an actuating system keeping the moving pad        in the disengaged position against the elastic biasing member in        the active configuration.

An aircraft is also provided comprising a plurality of sources forvarying the mechanical energy of the aircraft comprising at least onepropulsion motor and at least one member for modifying the energy of theaircraft;

-   -   a flight control unit,    -   a device as described above, the position sensor detecting the        position of the moving lever being connected to the flight        control unit, the flight control unit being able to pilot,        jointly, at least one propulsion motor and at least one member        for modifying the energy of the aircraft based on the position        information of the moving lever in the guide.

The aircraft may comprise one or more of the following features,considered alone or according to any technically possible combination:

-   -   the flight control unit is able to determine, at each moment, a        range of available mechanical energy variations able to be        obtained using sources for varying the mechanical energy of the        aircraft, and to enslave the position of the moving lever via        the active system for applying force in a movable neutral        position representative of a current mechanical energy variation        of the aircraft in the range of possible mechanical energy        variations for the aircraft;    -   the flight control unit is able to control the active force        application system to generate a plurality of different applied        force profiles based on a movement context of the aircraft;    -   at least one first source piloted by the flight control unit        based on position information of the moving lever being a motor,        at least one second source piloted by the flight control unit        jointly with the first source based on the position information        of the moving lever being a member for modifying the mechanical        energy of the aircraft;

A method for controlling an aircraft is also provided, comprising thefollowing steps:

-   -   providing a device as previously described, the moving lever        occupying a given position in the guide;    -   sending position information of the moving lever generated by        the position sensor to a flight control unit;    -   joint piloting, based on the position information of the moving        lever, of at least one propulsion motor and at least one member        for modifying the energy of the aircraft;    -   generating a force applied on the moving lever by the system for        applying a force, the applied force depending on at least the        position of the moving lever in the guide.

The method may comprise one or more of the following features,considered alone or according to any technically possible combination:

-   -   the management device includes an auxiliary assembly for        applying a mechanical force on the moving lever, the auxiliary        application assembly switching automatically from a deactivated        configuration when the active system for applying a force is        active to an active configuration, when the active system for        applying a force is deactivated.

BRIEF SUMMARY OF THE DRAWINGS

The invention will be better understood upon reading the followingdescription, provided solely as an example and done in reference to theappended drawings, in which:

FIG. 1 is a block diagram schematically showing an aircraft providedwith a first energy management device according to an embodiment of theinvention;

FIG. 2 is a three-quarters front perspective view of the main elementsof the energy management device of FIG. 1, including a centralizedcontrol lever for the total mechanical energy of the aircraft and anactive system for applying a force on the centralized control lever, aswell as individual levers;

FIGS. 3 and 4 illustrate an assembly for applying a mechanical backupforce on a centralized control lever of the energy management device ofFIG. 1;

FIGS. 5 and 6 illustrate individual control levers of each motor,intended to supplement the centralized control lever in case ofoperating defect of the centralized control lever;

FIG. 7 shows light strips able to display light indications depending onthe movement context of the aircraft;

FIG. 8 is a block diagram similar to that of FIG. 1, illustrating thecontrol of the light strips of FIG. 7;

FIGS. 9 to 11 illustrate various force profiles that can be applied onthe centralized control lever based on the position of the centralizedcontrol lever by the active application system;

FIGS. 12 to 14 illustrate different display configurations of an lightindication on the light strips.

DETAILED DESCRIPTION

A first aircraft 10 provided with a mechanical energy management device12 according to an embodiment of the invention is illustrated by FIG. 1.

Aside from the mechanical energy management device 12, the aircraft 10includes several propulsion motors 14, members 16 for modifying themechanical energy of the aircraft 10, sensors 17 for measuring flightparameters, and a flight control unit 18, able to control each of themotors 14 and the mechanical energy modifying members 16.

Each propulsion motor 14 is able to be controlled by the flight controlunit 18, to cause a thrust force on the aircraft 10 to change,increasing or decreasing the total mechanical energy of the aircraft 10.

The mechanical energy modifying members 16 are advantageously membersfor modifying the drag of the aircraft 10. They for example include airbrakes and/or deployable foil flaps. Each member for modifying themechanical energy is able to be controlled by the flight control unit18, to cause a drag force on the aircraft 10 to change, decreasing orincreasing the total mechanical energy of the aircraft 10.

Each propulsion motor 14 and each member for modifying the mechanicalenergy 16 therefore make up a mechanical energy variation source of theaircraft 10.

The flight parameter measuring sensors 17 are in particular able todetermine the position, the altitude, the air and ground speeds, and theair and ground gradients.

The flight control unit 18 includes at least one processor 20, and amemory 22 containing a plurality of software modules 24 to 28 capable ofbeing executed by the processor 20.

The memory 22 in particular contains a module 24 for developing controlsignals of the motors 14 and control signals of the members formodifying the mechanical energy 16.

It advantageously contains a module 26 for calculating a propertyrepresentative of the mechanical energy variation of the aircraft basedon flight parameters.

It further contains a module 28 for controlling the position of a movinglever 30 of the energy management device 12, able to define a positionof the moving lever 30 representative of the situation of the aircraft10 in its range of energy variation capacities.

The module 24 for developing control signals is able to calculate thecontrol signals of the motors 14 and of the energy modifying members 16based on a set point received from the energy management device 12, whenthe aircraft 10 is in manual piloting mode, or based on a set pointreceived from an automatic piloting system, when the aircraft 10 is anautomatic piloting mode.

The module 26 for calculating the property representative of themechanical energy variation is for example able to calculate a currentmechanical energy variation of the aircraft and a range of mechanicalenergy variations that can be achieved by the aircraft 10 at eachmoment, based on flight parameters obtained from the sensors 17, and theoperational situation of the aircraft.

The operational situation of the aircraft 10 in particular includes themovement of the aircraft 10 on the ground or in flight and the availableequipment, in particular the number of motors 14, the individual thrustdeveloped by each motor 14, the number of mechanical energy modifyingmembers 16 and the position of each mechanical energy modifying member16.

The property representative of the mechanical energy variation is forexample a pseudo-total gradient, as calculated in U.S. Pat. No.8,527,173 by the Applicant, the details of the calculation of U.S. Pat.No. 8,527,173 being hereby incorporated by reference herein. Thispseudo-total gradient is defined as the ground gradient, which, undercurrent conditions, leads to a constant conventional speed.

This pseudo-total gradient γ* is for example calculated using thefollowing formula:

$\gamma^{*} = {{\gamma_{sol} + {\frac{\left( \frac{\partial V_{air}}{\partial V_{c}} \right)_{z = {cste}}}{1 + {\frac{V_{sol}}{g} \cdot \left( \frac{\partial V_{air}}{\partial z} \right)_{{Vc} = {cste}}}}\frac{{\overset{.}{V}}_{c}}{g}}} = {\gamma_{sol} + {K \cdot \frac{{\overset{.}{V}}_{c}}{g}}}}$

where γ_(sol) is the ground gradient of the aircraft 10, V_(sol) is thespeed of the aircraft 10 relative to the ground, V_(air) is the airspeedof the aircraft 10, V_(C) is the conventional speed of the aircraft 10,g is the gravitational acceleration, and z is the altitude of theaircraft 10.

As will be seen below, the module 28 for controlling the position of themoving lever 30 is able to develop a position control signal of themoving lever 30 as a function of the current mechanical energyvariation, and the range of mechanical energy variations that can beachieved by the aircraft 10.

The calculated position of the moving lever 30 reflects the currentmechanical energy variation of the aircraft 10 in the range ofmechanical energy variations that can be achieved by the aircraft 10.This position is referred to as a “movable neutral” position, and variesover time, without user intervention depending on the movementconfiguration of the aircraft 10, in the automatic piloting mode.

The bounds of the range of mechanical energy variations that can beachieved also vary over time as a function of the situation of theaircraft (in particular position, speed, attitude, available thrust,available drag, etc.).

The maintaining of the current mechanical energy variation of theaircraft 10, and therefore the movable neutral position, isadvantageously enslaved by the automatic piloting system in automaticpilot mode.

The mechanical energy variation of the aircraft 10 can also be adjustedmanually by the pilot by shifting the moving lever 30 away from themovable neutral position to define a new desired mechanical energyvariation set point of the aircraft 10, in the range of mechanicalenergy variations able to be achieved by the aircraft 10.

Each position of the moving lever 30 then corresponds to a mechanicalenergy variation setpoint value of the aircraft 10.

In reference to FIGS. 1 and 2, the energy management device 12 includesa main energy management system 32 comprising the moving lever 30, anauxiliary individual control system 34 of the motors 14, able to be usedby the user if the moving lever 30 fails, and an illuminated displaysystem 36, visible in FIG. 8, able to provide light indications to theuser of the moving lever 30.

In reference to FIG. 2, the main energy management system 32 includes asupport 40, intended to be fixed in the cockpit of the aircraft 10, themoving lever 30, mounted moving in the support 40, and at least oneposition sensor 42, intended to measure the position of the moving lever30 relative to the support 40.

The main energy management system 32 further includes an active system44 for applying a force on the moving lever 30, piloted by the flightcontrol unit 18, and advantageously an auxiliary assembly 46 forapplying a mechanical force on the moving lever 30, able to operate incase of malfunction of the active system 44.

Advantageously, the main energy management system 32 further includes asurpassable mechanical stop system 48.

The support 40 is able to be placed in the cockpit of the aircraft 10,preferably between the seats of the cockpit, in the central pylon.

As illustrated by FIG. 2, the support 40 includes an open-worked base50, and an upper cover 52 mounted on the base 50, through which themoving lever 30 is engaged.

The base 50 defines an inner volume 54, through which a lower part ofthe moving lever 30 is inserted.

The upper cover 52 upwardly closes the base 50. Here, it has an upwardlycurved upper surface 56. It defines a longitudinal guide 58 for guidingthe movement of the moving lever 30.

The moving lever 30 is a centralized control lever that is able tocontrol a mechanical energy variation of the aircraft 10, withoutpiloting one particular motor 14 of the aircraft 10 individually. Theposition of the moving lever 30 in the guide 58 measured by the positionsensor 42 is transmitted to the flight control unit 18 to generate acontrol signal acting jointly on several motors 14 of the aircraftand/or on the energy modifying members 16.

In reference to FIG. 2, the moving lever 30 includes a rod 60 engagedthrough the guide 58, a head 62 mounted at the upper end of the rod 60to be grasped by the hand of a user of the device 12, and a sector 64,secured to the lower end of the rod 60, in the inner volume 54.

In this example, the moving lever 30 further includes sliding flaps 66closing off the guide 58, to prevent objects from passing through theguide 58 toward the inner volume 54.

In the example shown in FIG. 2, the rod 60 has, at its lower end, ahorizontal bush 68 receiving a horizontal rotation axis 70 of the movinglever 30, perpendicular to the longitudinal axis A-A′ of the guide 58.

The head 62 protrudes forward at the upper end of the rod 60. It definesan upper bearing surface 71 for the palm of the user's hand and a lowergrasping surface 72 by the user's fingers. Here, it is provided withcontrol buttons 74, for example for airbrake controls, or the flightmode.

The sector 64 is mounted on the lower end of the rod 60, around the axis70. It extends in a plane perpendicular to the axis 70.

As will be seen below, it is able to cooperate mechanically with theauxiliary end 46 for applying a mechanical force, in case of failure ofthe active application system 44.

The bush 68 has a radial finger 74 protruding transversely relative tothe axis 70 to cooperate with the active system 44 for applying a forceon the moving lever 30.

The moving lever 30 is thus rotatable around the axis 70 in the guide 58between a rear extreme position and a forward extreme position.

The position sensor 42 is able to determine information relative to theangular position of the moving lever 30 around the axis 70, and to sendthis signal to the flight control unit 18.

The active system for applying a force 44 includes an actuator 80, and amechanism 82 for transmitting movement between the actuator 80 and themoving lever 30. It comprises a control unit 84 of the actuator 80,visible in FIG. 1, connected to the flight control unit 18, to controlthe force applied on the moving lever 30 and the movement of the movinglever 30 in the guide 58.

The actuator 80 here includes an electric motor 86, provided with anoutput shaft 88 rotating around a motor axis B-B.

The motor 86 is preferably a brushless motor. It is electricallyconnected to the control unit 84 of the actuator 80, which controls therotation of the shaft 88 in one direction or the other around the axisB-B′.

In reference to FIGS. 1 and 2, the transmission mechanism 82advantageously includes a reducing gear 90, mounted at the output of theshaft 88, a finger 92 rotating jointly with the output of the reducinggear 90 around the axis B-B′, and a transmission connecting rod 94,inserted between the rotating finger 92 and the radial finger 74 of thesector 64 of the moving lever 30.

The connecting rod 94 has a first end 96 articulated upstream on therotating finger 92, and a second end 98 articulated downstream on theradial finger 74. It is able to convert and transmit the rotationalmovement generated by the motor 80 on the shaft 88 around the axis B-B′into a rotating movement of the moving lever 30 around its axis 70.

The presence of a transmission mechanism 82 provided with a connectingrod 94 provides a very flexible movement without mechanical play of themoving lever 30. Furthermore, the positioning of the motor 86 relativeto the lever 30 is freer than in a system comprising gears, whichoptimizes the available space to position the device 12.

The control unit 84 of the actuator 80 is able to receive, in real-time,the control signals developed by the control module 28 of the positionof the moving lever 30, and to transcribe these control signals into amovement of the moving lever 30 in the guide 58.

In particular, the control unit 84 is able to pilot the actuator 80 togenerate a force shifting the moving lever 30 between its rear extremeand forward extreme positions, following the calculated movable neutralposition, in the absence of action by the user on the moving lever 30.This force in particular depends on the position of the moving lever 30in the guide 58.

The control unit 84 is further able to create a force applied on themoving lever 30 when the user grasps the moving lever 30 and moves itaround its axis 70 to pilot the mechanical energy variation of theaircraft 10 manually.

The applied force controlled by the control unit 84 depends on theposition of the moving lever 30 between its rear extreme position andits forward extreme position. It also depends on the movement context ofthe aircraft 10, and the available energy variation in the aircraft 10,as calculated by the module 26.

In particular, the control unit 84 is able to generate variable forceprofiles during the shifting of the moving lever 30 around its axis 70.Examples of variable profiles as a function of the angular position P ofthe moving lever 30 are shown in FIGS. 9 to 11.

In the example of FIG. 9, the variable profile comprises a ramp 100, theapplied force having an increasing intensity when the moving lever 30moves toward its forward extreme position.

In the example of FIG. 10, the variable profile comprises a stabledetent 102 around a given position P1 between the rear extreme positionand the forward extreme position. Once switched into the stable detent102, the moving lever 30 is able to remain in this position, since theuser must cross a wall in the forward or rear direction to leave thisposition.

In the example of FIG. 11, the variable profile comprises an unstabledetent 104, in position P1, in which the user must cross a wall to passposition P1, without being able to remain stably in this position.

The control unit 84 is able to adapt the force profile generated on themoving lever 30 at any moment, for example the intensity of the ramps100, and/or the position, the intensity/height, and/or the nature of thedetents 102, 104 as a function of the control signals received from theflight control unit 18, and the position of the moving lever 30.

In the embodiment of FIG. 1, the control unit 84 includes a real-timeelectronic board 106, connected to the flight control unit 18, and anelectronic control unit (ECU) of the motor 108 inserted between thereal-time electronic board 106 and the electric motor 86.

The real-time electronic board 106 for example includes a processor anda memory, having modules for transcribing control signals received fromthe unit 18 into corresponding force profiles to be applied on themoving lever 30. The electronic control unit of the motor 108 is able tocreate electric control pulses, based on the raw order received from theboard 106.

It is electrically connected to the motor 86 to send the generatedpulses to the motor 86.

The auxiliary assembly 46 for applying a mechanical force on the movinglever 30 is intended to offset a defect of the active system forapplying a force 44, for example in the absence of power supply of theactive system for applying a force 44. It is able to switch between adeactivated configuration when the active system for applying a force 44is active and an active configuration, when the active system forapplying a force 44 is deactivated.

In reference to FIGS. 3 and 4, the auxiliary assembly 46 includes atleast one pad 110 for mechanical cooperation with the moving lever 30,movable between a position engaged on the moving lever 30, in the activeconfiguration of the auxiliary assembly 46 and a position disengagedfrom the moving lever 30 in the deactivated configuration of theauxiliary assembly 46.

The auxiliary assembly 46 further includes a member 112 for elasticallybiasing each pad 110 toward its engaged position, and an actuatingsystem 114 able to keep the pad 110 in the disengaged position, againstthe elastic biasing member 112.

The pad 110 is mounted translatably along an axis parallel to therotation axis 70 of the moving lever 30, in a cylinder 113 mounted fixedrelative to the support 40, between the engaged position and thedisengaged position.

In its engaged position, the pad 110 presses on a side surface of thesector 64 of the moving lever 30, thus generating a friction forcebetween the pad 110 and the moving lever 30. In its released position,the pad 110 has been moved away from the side surface of the sector 64,and no longer mechanically cooperates with the moving lever 30.

The elastic biasing member 112 is housed in the sleeve 113 between thesleeve 113 and the pad 110. By default, it is able to stress the pad 110toward its engaged position. It is for example formed by a helicalspring.

The actuating system 114 includes a moving rod 116, and an element 118for moving and maintaining the rod 116 in a deployed position. Itfurther includes a rotary lever 118A and a prong 118B connecting thelever 118A to the pad 110.

The lever 118A is mounted pivoting relative to this support 40 around anaxis C-C′ perpendicular to and not secant with the rotation axis 70 ofthe moving lever 30.

The prong 118B is articulated at a first end on the lever 118A. It isreceived at a second end in a housing of the pad 110.

In the presence of a power supply of the moving and maintaining element118, the rod 116 in its deployed position is able to cooperate with thelever 118A to keep the pad 110 in its disengaged position against theelastic biasing force generated by the elastic biasing member 112, usingthe prong 118B.

When there is no power supply for the moving and maintaining element118, the rod 116 retracts, and no longer cooperates with the lever 118A.The elastic biasing member 112 then deploys the pad 110 outside thechamber 113 and then presses the pad 110 against the sector 64 of themoving lever 30.

The mechanical stop system 48 includes a stop 120 moving jointly withthe moving lever 30 and a switch 121 secured to the support 40 tocooperate mechanically with the stop 120 in an intermediate position ofthe moving lever 30 between the forward extreme position and the rearextreme position.

In reference to FIG. 4, the mechanical stop system 48 further includes asecond mechanical stop for passing in a rear sector of the travel, and acontrol 122 for passage of the second stop, visible in FIG. 2, forexample an unlocking vane mounted moving on the rod 60 of the controlstick 30 below the head 62.

The mechanical stop system 48 is thus able to embody particular controlregions of the moving lever 30, between the intermediate position andthe rear extreme position of the moving lever 30, for example a controlzone of the thrust reversers.

The auxiliary system 34 for individual control of the motors 14 isillustrated by FIGS. 2, 5 and 6.

As illustrated by these figures, it is mounted adjacent to the mainenergy management system 32, for example behind the latter, in thelongitudinal extension of the support 40.

The auxiliary control system 34 includes an auxiliary support 130, and aplurality of individual control levers 132 of each motor 14. It alsoincludes, for each control lever 132, one or several additional sensors134 detecting the position of the individual control lever 132.

Advantageously, the auxiliary control system 34 further includes acooperation mechanism 136 between the individual control levers 132(visible in FIG. 6), and an auxiliary mechanical stop system 138 on eachindividual control lever 132.

In this example, the additional support 130 includes, for eachindividual control lever 132, a guide 140 for the movement of the lever132.

The guides 140 extend parallel to a same longitudinal direction sharedwith that of the guide 58. They are adjacent to one another.

Each individual lever 132 includes a rod 142 and a head 144, mounted atan upper end of the rod 142. Each individual lever 132 furtheradvantageously comprises a protective flap 148 closing off the guide140.

In reference to FIG. 6, the head 144 includes a central body 150,mounted on the upper end of the rod 142, and longitudinal graspingfingers 152, protruding longitudinally in front of and behind thecentral body 150.

The central body 150 protrudes upward relative to the finger 152. Itdefines an axial housing 154 for receiving a light indicator and sidehousings 156 for receiving a cooperation mechanism 136.

Each finger 152 has an end 158 in the form of a hook oriented downward.This end 158 is easy to grasp by the finger of a user inserted below thehook 158 either to lift the individual lever 132, or to move it forwardor backward.

In this example, the individual lever 132 is mounted rotating around anaxis D-D′ parallel to the rotation axis 70 of the moving lever 30,between a punctual rear position in the guide 140, a plurality ofintermediate positions in the guide 140, between two stops of theauxiliary stop system 138, and a punctual forward position.

In the punctual forward position and the punctual rear position, eachindividual lever 132 is blocked in rotation around its axis D-D′ by astop. Each individual lever 132 is able to be moved upward along theaxis of its rod 142 to pass the stop and reach an intermediate position.

In the forward punctual position, each individual lever 132 thenoccupies an idle position, in which the motor 14 associated with theindividual lever 132 is controlled by the flight control unit 18 jointlywith the other motors 14, based on the position of the moving lever 30,without using the position of the moving lever 132.

In each of the intermediate positions between the forward punctualposition and the rear punctual position, the motor 14 associated withthe individual lever 132 is controlled individually by the flightcontrol unit 18 based on the position of the individual lever 132,without using the position of the moving lever 30. The individual lever132 is movable continuously without having to lift it.

The rear punctual position advantageously corresponds to the activationof the thrust reverser, or extinguishing of the motor.

Each additional position sensor 134 is able to determine informationrelative to the angular position of an associated individual lever 132around the axis D-D′, and to send this signal to the flight control unit18.

The cooperating mechanism 136 is inserted between each pair of adjacentindividual levers 132. For example, it includes a transverselyretractable ball and a receptacle for the ball, respectively housed inside housings 156 across from two adjacent heads 144.

When the ball of the head 144 of a lever 132 is received in thecorresponding receptacle of the head 144 of an adjacent lever 132, thelevers 132 are movable jointly with one another in rotation around theaxis D-D′.

The ball is able to retract when a shearing force is applied between theadjacent heads 144 of two levers 132. In this case, each of the twoindividual levers 132 in each intermediate position becomes rotatableagain around its axis D-D′, independently of the other individual lever132.

The flight control unit 18 is able to detect that an individual lever132 has been moved away from its forward punctual position, to activatethe individual control of the motor 14 corresponding to the individuallever 132 and to adjust the speed of the motor 14, and in particular thethrust, as a function of the angular position of the individual lever132 in each intermediate position.

Thus, the auxiliary control system 34 of the motors 14 is able to beactivated by a user of the energy management device 12 when the mainenergy management system 32 fails. It is able to allow the individualcontrol of each motor 14 from a corresponding individual lever 132.

In reference to FIGS. 7 and 8, the illuminated display system 36includes at least one light strip 170, arranged near the centralizedcontrol lever 30, and a control unit 172 of each light strip 170, ableto display at least one light indication at least at one given point ofthe light strip 170. The position of the or each given point isdetermined by the flight control unit 18 and is translated by thecontrol unit 172 into an electrical signal to produce the lightindication, based on the movement context of the aircraft 10, inparticular as a function of the total mechanical energy variation of theaircraft 10, calculated at each moment by the flight control unit 18.

In the example shown in FIG. 7, the illuminated display system 36includes two parallel light strips 170, arranged longitudinally oneither side of the moving lever 30, parallel to the guide 58.

Each light strip 170 extends over at least part of the length of theguide 58, preferably over the entire travel of the centralized controllever 30 in the guide 58 between the forward extreme position and therear extreme position.

Each light strip 170 here is formed by a series of light sources 174arranged linearly. Each light source 174 is able to go from an off stateto at least one illuminated state, preferably a plurality of illuminatedstates with different colors and/or intensities and/or sequences.

Advantageously, each light source 174 is formed by a light-emittingdiode. Alternatively, the light sources 174 are formed on a screen. Thelight sources are formed directly on the screen or by backlighting on astrip light.

The strip 170 defines more than two light sources 174 corresponding tosuccessive positions of the control lever 30 along its travel in theguide 58.

The control unit 172 of each light strip 170 is connected to the flightcontrol unit 18 via the control unit 84 of the active force applyingsystem 44. It is able to control each light source 174 of the light 170between the off state and the illuminated state(s), based on themovement context of the aircraft 10, in particular based on theavailable mechanical energy variation for the aircraft 10.

Depending on its state, in particular its color, its intensity and/orits elimination sequence, the light source 174 provides a lightindication at the point of the light strip 170 where it is situated.

Advantageously, the control unit 172 of the light strip 170 is able todisplay a first light indication at least at a first point of the lightstrip 170 via at least one first light source 174 and at least onesecond light indication, separate from the first light indication, atleast at one second point of the strip, via at least one second lightsource 174 separate from the first light source 174.

The first light indication and the second light indication are colors,with different intensities and/or sequences.

The control unit 172 of the light strip 170 is able, in a first movementcontext of the aircraft, to place a particular light indication at leastat one given point of the light strip 170, at a first light source 174,and in a second movement context of the aircraft, to place the sameparticular light indication at least at one other given point of thelight strip, at a second source 174.

Preferably, the flight control unit 18 is able to calculate, at eachmoment, the position of the given point as a function of the movementcontext of the aircraft 10 at that moment, and to send this position tothe control unit 172.

Advantageously, the control unit 172 of the light strip 170 is able toplace a first light indication on a light segment 176 of the light strip170 formed by a plurality of successive light sources 174.

The successive light sources 174 of the light segment 176 display thesame light indication, for example the same color, the same intensityand/or the same light sequence.

For example, in a movement context of the aircraft 10 corresponding to arange of available mechanical energy variations calculated at eachmoment, the control unit 172 of the light strip 170 is able to display afirst particular light indication on a light segment 176 of the lightstrip 170 corresponding to the range of available mechanical energyvariations that can be controlled with the moving lever 30.

The light segment 176 corresponds to the possible movement of the movinglever 30 in the particular movement context of the aircraft 10, in viewof the available mechanical energy variation at that moment.

Thus, the pilot not only has information about movement possibilitiesbased on the shift in the position of the moving lever 30 along themovable neutral position, but also a visual indication of mechanicalenergy variations that may be achieved by actuating the moving lever 30,by visually inspecting the light strip 170.

As illustrated by FIGS. 12 to 14, the control unit 172 of the lightstrip 170 is able to vary the length and the position of the lightsegment 176 as a function of the movement context of the aircraft, andin particular as a function of the available mechanical energy variationfor the aircraft 10.

Thus, the first light indication embodied by the light segment 176 inFIG. 12 moves along the light strip in FIG. 13. The length of the lightsegment 176 varies between FIG. 12 and FIG. 13.

The first particular light indication has its own specific color,intensity and/or light sequence, for example a green color, a constantintensity and a continuous light sequence.

Furthermore, the control unit 172 of the light strip 170 is able todisplay a second particular light indication arranged across from theposition of a movement detent of the moving lever 30 in the guide 52.

The second particular light indication for example has a color, anintensity and/or a light sequence different from the first lightindication.

For example, the control unit 172 of the light strip 170 is able todisplay a second particular light indication at the ends 178 of thelight segment 176 having the first light indication.

Advantageously, the position of the second light indication correspondsto that of a detent or a stop generated by the control unit 84. Thus,the pilot has a dual tactile and visual indication, for examplecorresponding to a particular point of the range of mechanical energyvariations available for the aircraft 10.

The control unit 172 of the light strip 170 is advantageously able todisplay a third particular light indication at a fixed point 180 of thestrip, for example corresponding to the position in which the movinglever 30 reaches a mechanical stop of the stop system 48.

Advantageously, in reference to FIG. 6, the illuminated display system36 further includes, for each individual lever 132 corresponding to amotor 14, an additional light source 190, able to generate a lightindicator representative of the operating state of the motor 14.

The light indicator has a first state, for example a first color, whenthe motor 14 is functional, and a second state, for example a secondcolor, when the motor 14 has a malfunction.

The additional source 190 here is housed in the axial housing 154present on the head 144 of the lever 132. It is for example formed by alight-emitting diode.

The operation of the energy management device 12 will now be described.

Once the device 12 is activated, after turning on the motors 14, theauxiliary assembly 46 for applying a mechanical force on the centralizedcontrol lever 30 moves into its deactivated position. The rod 116 of theactuating system 114 is deployed and exerts a force on the elasticbiasing member 112, separating the pads 110 from the moving lever 30.

At each moment, on the ground and during flight, the calculating module26 of the flight control unit 18 calculates the current mechanicalenergy variation of the aircraft 10 and the possible mechanical energyvariation range as a function of the available thrust at the motors 14,the availability of the energy modifying members 16, and movementparameters of the aircraft 10.

The calculating module 28 of the flight control unit 18 then determinesthe “movable neutral” position of the moving lever 30 as a function ofthe total mechanical energy variation of the aircraft 10 at each moment,and the total mechanical energy variation range that may be achieved bythe aircraft 10 at that moment.

The active system 44 for applying a force on the moving lever 30 thenreceives, from the flight control unit 18, via the control unit 84, aset-point to shift the moving lever 30.

The electric motor 86 of the actuator 80 becomes activated under theeffect of the control unit 84 to rotate the output shaft 88 andtransmits the movement to the connecting rod 94 via the reducing gear 90and the rotating finger 92.

The movement of the connecting rod 94 at its first end 96 is transmittedto its second end 98 at the sector 64 of the moving lever 30 to generatea force shifting the moving lever 30 that in particular depends on theposition of the moving lever 30 in the guide 58. The moving lever 30 isrotated around its axis 70 to follow the position of the moving neutral.

The movement of the moving lever 30 is therefore enslaved by the flightcontrol unit 18 in this automatic pilot mode.

Thus, the position of the moving lever 30 in the guide 58 corresponds,at each moment, to the evolution potential of the current mechanicalenergy variation of the aircraft 10.

When the pilot wishes to modify the mechanical energy of the aircraft 10manually, he grasps the moving lever 30 and moves it in the guide 58. Ateach moment, the position sensor 42 determines the angular position ofthe moving lever 30 around its axis 70. This angular position istransmitted to the flight control unit 18, which develops a controlsignal of the propulsion motors 14 and of the energy modifying members16 as a function of the position of the moving lever 30 detected by theposition sensor 42.

Furthermore, when the pilot shifts the moving lever 30 away from itsmovable neutral position, the active system for applying a force 44applies a force profile on the moving lever 30 that in particulardepends on the position of the moving lever 30 in the guide 58. Theelectric motor 86 is controlled by the control unit 84, to transmit amovement to the reducing gear 90, the finger 92, then the connecting rod94 and the sector 64.

The control unit 84 generates a variable force profile during themovement of the moving lever 30 around its axis 70, for example a ramp100 having a force with an increasing intensity as a function of atleast the position of the moving lever 30 in the guide 58 when themoving lever 30 moves toward the forward extreme position (see FIG. 9),a stable detent 102 around a given position P1 between the rear extremeposition and the forward extreme position (see FIG. 10) and/or anunstable detent 104 around the position P1 (see FIG. 11).

Thus, the pilot is guided at all times in actuating the moving lever 30,and can intuitively anticipate the operating bounds in terms ofavailable energy on the aircraft 10.

Once the lever 30 is positioned at the desired mechanical energyvariation setpoint by the pilot, a new movable neutral positioncorresponding to this in-flight mechanical energy variation isdetermined by the control module 28 at each moment.

The pilot can also keep the lever 30 in position against a set-pointfrom the automatic piloting system seeking to move it to adjust theposition of the movable neutral.

In case of power failure of the active system 44 for applying a force,the actuating system 114 is no longer supplied with electricity. The rod116 retracts and the elastic biasing member 112 returns each pad 110 toits position engaged on the moving lever 30.

Each pad 110 then exerts a mechanical force on the sector 64 of themoving lever 30 to keep the moving lever 30 in a stable position,without interaction by the pilot with the moving lever 30. Furthermore,when the pilot grasps the moving lever 30, the mechanical force exertedby the pads 110 on the moving lever 30 can be overcome, while ensuringprecise guiding of the moving lever 30 during its movement in the guide58. The position information of the moving lever 30 then remainsavailable for the flight control unit 18.

During the normal operation of the moving lever 30, the individuallevers 132 of the auxiliary energy management system 34 are kept intheir idle positions, here in their forward punctual positions.

In case of incident preventing the maneuvering of the moving lever 30,for example in case of mechanical blocking of the moving lever 30, thepilot lifts each individual lever 132 on its axis, then rotates ittoward the rear to pass the stop. The passage of the stop activates theauxiliary energy management system 34.

Advantageously, this movement is obtained by sliding the pilot's fingersbelow the hook-shaped ends of the fingers 152 of each head 144 of thelevers 132.

Then, the pilot moves each individual lever 132 from its forwardpunctual position to an intermediate setpoint position.

By default, the cooperation mechanism 136 between the individual levers132 is active, such that the individual levers 132 move jointly with oneanother. Alternatively, when the pilot wishes to control each of themotors 14 of the aircraft individually, for example when one of themotors fails, he deactivates the cooperation mechanism 136 and actuateseach lever 132 individually by giving it its own position.

Said auxiliary energy management system 34 is therefore suitable forsupplementing a failure of the main energy management system 32 andallows the pilot to control each motor 14 of the aircraft 10individually. The energy management device 12 therefore providesredundancy for functions in terms of the propulsion of the aircraft 10.

Simultaneously, based on a set-point given by the flight control unit18, the control unit 172 of the light strip 170 places at least onelight indication at least at one given point of the light strip 170calculated at each moment by the control unit 172 based on the movementcontext of the aircraft 10, in particular as a function of the totalmechanical energy of the aircraft 10.

Advantageously, the control unit 172 of the light strip 170 places aparticular light indication on a light segment 176 of the light strip170 formed by a plurality of successive light sources 174. Thesuccessive light sources 174 of the light segment 176 preferably displaythe same light indication, for example the same color, the sameintensity and/or the same light sequence.

As illustrated in FIGS. 12 to 14, in a movement context of the aircraft10 corresponding to an available mechanical energy variation calculatedat each moment, the control unit 172 of the light strip 170 displays afirst particular light indication on a light segment 176 of the lightstrip 170 corresponding to the range of available mechanical energyvariations that can be controlled with the moving lever 30.

The control unit 172 of the light strip 170 varies the length (see FIG.14) and the position (see FIG. 13) of the light segment 176 as afunction of the movement context of the aircraft 10, and in particularas a function of the available mechanical energy variation for theaircraft 10.

The first particular light indication has its own specific color,intensity and/or light sequence, for example a green color, a constantintensity and a continuous light sequence.

Furthermore, the control unit 172 of the light strip 170 displays asecond particular light indication across from the position of amovement detent of the centralized control lever 30 in the guide 52.

The second particular light indication has a color, an intensity and/ora light sequence different from the first light indication.

For example, the control unit 172 of the light strip 170 displays asecond particular light indication at the ends 178 of the light segment176 having the first particular light indication.

The control unit 172 of the light strip 170 advantageously displays athird particular light indication at a fixed point 180 of the strip, forexample corresponding to the position in which the moving lever 30reaches a mechanical stop of the stop system 48.

Thus, at any moment, the pilot views the movement range at his disposalwith the moving lever 30, corresponding to the mechanical energyvariation achievable by the aircraft 10, using the first lightindication displayed on the entire light segment 176.

The pilot further views the bounds of the movement of the moving lever30 owing to the second light indication, displayed at the ends 178 ofthe light segment 176.

Lastly, the pilot advantageously views the position of a mechanical stopowing to the third light indication displayed in the fixed position 180of this stop.

The length and the position of the light segment 176 forming the firstlight indication, and the position of its ends 178, forming the secondlight indication, is able to evolve over time, as a function of themovement context of the aircraft 10, and particularly as a function ofthe available mechanical energy variation for the aircraft 10.

The display system 36 is therefore particularly useful for the pilot ofthe aircraft 10, to perceive the energy available for the aircraft 10.

In one particular operating mode of the device 12, an optimizedmechanical energy variation value of the aircraft 10 is indicated to thepilot based on the movement phase of the aircraft 10.

For example, when the aircraft 10 prepares for takeoff, an optimizedmechanical energy variation value (here corresponding to an optimalthrust) is determined by the flight control unit 18, in particular as afunction of the mass of the aircraft 10 and the length of the runway. Aparticular light indication is displayed on a point of the light strip170 by the control unit 172 across from the position of the lever 30corresponding to the optimized mechanical energy variation set point.Likewise, the control unit 84 advantageously generates a particularforce profile in this position of the lever 30, for example a detent.

In one alternative, the movable neutral position is not necessarilydetermined as a function of the available mechanical energy variationfor the aircraft 10.

In one embodiment, all of the motors 14 and the mechanical energymodifying members 16 are able to be controlled jointly by the flightcontrol unit 18 as a function of the position of the moving lever 30.

Alternatively, for a single-engine aircraft 10 or when a motor 14 of theaircraft 10 has been turned off (for example, using an individual lever132), the active motor 10 and the mechanical energy modifying members 16are able to be controlled jointly by the flight control unit 18 as afunction of the position information of the moving lever 30.

In one alternative, the energy management device 12 has no auxiliaryenergy management system 34 and/or has no display system 36.

What is claimed is:
 1. A device for managing the mechanical energy of an aircraft, the device being configured for placement in a cockpit of the aircraft and comprising: a support defining a guide; a moving controller configured for controlling a mechanical energy variation of the aircraft, the moving controller being mounted movably through the guide; at least one position sensor configured for detecting a position of the moving controller in the guide, the at least one position sensor being configured to create position information for the position of the moving controller in the guide for sending to a flight control unit of the aircraft, the flight control unit being configured to control jointly, based on position information of the moving controller, at least one propulsion motor and at least one member configured for modifying the drag of the aircraft; and an active force applicator configured for applying a force on the moving controller, the active force applicator being configured to generate the force applied on the moving controller, the applied force depending on at least the position of the moving controller in the guide.
 2. The device according to claim 1, wherein the active force applicator is configured to generate, in the absence of outside maneuvering of the moving controller by a user, a force for moving the moving controller in the guide to a movable neutral position.
 3. The device according to claim 2, wherein the movable neutral position is representative of a current mechanical energy variation of the aircraft in a range of possible mechanical energy variations for the aircraft.
 4. The device according to claim 1, wherein the active force applicator is configured to generate a force profile during maneuvering of the moving controller by a user.
 5. The device according to claim 4, wherein the force profile includes a stable detent, an unstable detent, and/or a ramp.
 6. The device according to claim 1, wherein the active force applicator comprises an actuator and an actuator control unit, the actuator being configured to act on the moving controller to generate the applied force, the actuator control unit being configured to control the actuator at least based on the position information of the moving controller.
 7. The device according to claim 6, wherein the actuator includes an actuator motor having an output shaft mounted for rotating around a shaft axis, the device further comprising a transmission mechanism connecting the actuator motor to the moving controller.
 8. The device according to claim 7, wherein the moving controller is mounted for rotating in the guide around a moving controller rotation axis non parallel to the shaft axis, the transmission mechanism comprising at least one intermediate connecting rod, having a first end jointly movable in rotation with the shaft axis and a second end jointly movable in rotation with the moving controller rotation axis.
 9. The device according to claim 1, comprising an auxiliary force applicator configured for applying a mechanical force on the moving controller, the auxiliary force applicator being configured to switch spontaneously between a deactivated configuration when the active force applicator for applying the force is active and an active configuration, when the active force applicator for applying the force is deactivated.
 10. The device according to claim 9, wherein the mechanical force is a friction force, the auxiliary force applicator for applying the mechanical force including at least one moving pad movable between a position engaged on the moving controller in the active configuration and a position disengaged from the moving controller in the deactivated configuration.
 11. The device according to claim 10, wherein the auxiliary force applicator for applying a mechanical force includes a biaser configured for elastically biasing the moving pad toward the engaged position and an actuator keeping the moving pad in the disengaged position against the biaser in the active configuration.
 12. An aircraft comprising: the device according to claim 1; a plurality of sources configured for varying the mechanical energy of the aircraft comprising the at least one propulsion motor and the at least one member configured for modifying the drag of the aircraft; and the flight control unit, the position sensor configured for detecting the position of the moving controller being connected to the flight control unit, the flight control unit being configured to jointly pilot the at least one propulsion motor and the at least one member for modifying the drag of the aircraft based on the position information of the moving controller in the guide.
 13. The aircraft according to claim 12, wherein the flight control unit is configured to determine, at each moment, a range of available mechanical energy variations configured to be obtained using the sources for varying the mechanical energy of the aircraft, and to enslave the position of the moving controller via the active force applicator for applying force in a movable neutral position representative of a current mechanical energy variation of the aircraft in the range of possible mechanical energy variations for the aircraft.
 14. The aircraft according to claim 12, wherein the flight control unit is configured to control the active force application force applicator to generate a plurality of different applied force profiles based on a movement context of the aircraft.
 15. A control method for an aircraft, comprising the following steps: providing the device according to claim 1, the moving controller occupying a given position in the guide; sending position information of the moving controller generated by the position sensor to the flight control unit; joint piloting, based on the position information of the moving controller, of the at least one propulsion motor and the at least one member configured for modifying the drag of the aircraft; generating a force applied on the moving controller by the active force applicator, the applied force being a function of at least the position of the moving controller in the guide.
 16. The method according to claim 15, wherein the management device includes an auxiliary force applicator configured for applying a mechanical force on the moving controller, the auxiliary application force applicator switching automatically from a deactivated configuration when the active force applicator for applying the force is active to an active configuration, when the active force applicator for applying the force is deactivated.
 17. A device for managing the mechanical energy of an aircraft, the device being configured for placement in a cockpit of the aircraft and comprising: a support defining a guide; a moving controller configured for controlling a mechanical energy variation of the aircraft, the moving controller being mounted movably through the guide; at least one position sensor configured for detecting a position of the moving controller in the guide, the at least one position sensor being configured to create position information for the position of the moving controller in the guide for sending to a flight control unit of the aircraft, the flight control unit being configured to control jointly, based on position information of the moving controller, at least one propulsion motor and at least one member configured for modifying the drag of the aircraft; an active force applicator configured for applying a force on the moving controller, the active force applicator being configured to generate the force applied on the moving controller, the applied force depending on at least the position of the moving controller in the guide; and an auxiliary force applicator configured for applying a friction force on the moving controller when the active force applicator for applying the force is deactivated.
 18. The device according to claim 1, wherein the moving controller is a moving control lever.
 19. The aircraft according to claim 12, wherein the moving controller is a moving control lever.
 20. The control method according to claim 15, wherein the moving controller is a moving control lever.
 21. The device according to claim 17, wherein the moving controller is a moving control lever. 